WO2001009553A1 - Dispositif de refroidissement par choc - Google Patents

Dispositif de refroidissement par choc Download PDF

Info

Publication number
WO2001009553A1
WO2001009553A1 PCT/EP2000/007387 EP0007387W WO0109553A1 WO 2001009553 A1 WO2001009553 A1 WO 2001009553A1 EP 0007387 W EP0007387 W EP 0007387W WO 0109553 A1 WO0109553 A1 WO 0109553A1
Authority
WO
WIPO (PCT)
Prior art keywords
coolant
cooling
component
cooled
baffle
Prior art date
Application number
PCT/EP2000/007387
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to US10/048,822 priority Critical patent/US6659714B1/en
Priority to JP2001513790A priority patent/JP2003532821A/ja
Priority to DE50008555T priority patent/DE50008555D1/de
Priority to EP00956359A priority patent/EP1409926B1/fr
Publication of WO2001009553A1 publication Critical patent/WO2001009553A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a device for a component to be cooled, in front of which a baffle cooling plate to which a coolant can be applied and with a coolant passage is arranged.
  • a discharge channel for the coolant is provided between the impact cooling plate and the component to be cooled.
  • a hot medium for example in a gas or steam turbine
  • a hot gas or steam places a high thermal load on the surfaces that delimit a room.
  • a hot gas or steam places a high thermal load on the surfaces that delimit a room.
  • the coolant required for cooling is usually taken as cooling air from a compressor coupled to the turbine. In order to keep the loss of efficiency associated with this cooling air extraction as low as possible, intensive searches are carried out for cooling concepts that ensure the most efficient use of coolant.
  • the turbine rotor blade comprises a blade root for attachment to a rotor of the turbine, an airfoil for flow around a working medium and a platform for delimiting a channel for the working medium.
  • a perforated wall element is therefore arranged in front of the side facing away from the hot working medium, which is referred to as an impact cooling plate.
  • a coolant passes through recesses (coolant feedthroughs) in the impact cooling plate and strikes the side of the platform facing away from the working medium. This cools the platform.
  • a coolable stator group for a gas turbine engine emerges from US Pat. No. 4,642,024.
  • the stator group has an outer air seal as well as an upstream holder and a downstream holder.
  • the brackets support the outer air seal with the help of hooks via a flow path for a hot working medium. This results in a structural division of the air seal into a downstream and an upstream edge region and a central region arranged between the edge regions.
  • an impingement cooling takes place in the central area.
  • Edge areas that are not directly exposed to cooling air due to the holders are cooled by passing a part of the collected cooling air through the holders in order to allow impingement cooling of the edge areas.
  • metering holes extend through the holders in order to guide the cooling air to the upstream and downstream edge regions for impingement cooling of the edge regions.
  • US-PS-5, 649, 806 discloses an improved cooling arrangement for guide rings of turbine guide vanes in a gas turbine.
  • a guide ring is arranged as a wall element in a gas turbine between the platforms of two turbine guide vanes.
  • the outer surface of the guide ring is exposed to the hot gas and is spaced in the radial direction from the outer ends of the turbine blades by a gap.
  • Heat is dissipated through cooling channels within the wall of the guide ring which is exposed to the hot gas convective cooling and made possible by impact cooling.
  • the guide to the outer surface has specially designed cooling air slots. These are oriented in such a way that the cooling air is led to the outer surface in the direction of flow of the hot gas with minimal momentum exchange between the cooling air and the hot gas. This causes film cooling of the surface exposed to the hot gas.
  • EP 0 624 757 A1 discloses an impact cooling direction for an aircraft engine component, for example a compressor part of an aircraft engine.
  • the impact cooling device comprises a corrugated sheet with a plurality of wave crests extending parallel to a preferred axis and adjacent wave troughs, each of which has a trapezoidal shape
  • the troughs are provided with baffle cooling holes. Cooling tunnels are formed by the wave troughs and the wave crests, which extend parallel to the preferred axis and are connected in the flow connection to the compressor part. Web-shaped distributor plates are arranged perpendicular to the preferred axis, the distributor plates being connected with their top edge to the perforated corrugated plate and with their bottom edge to the compressor outlet pipe. After baffle cooling of the compressor tube, the air is initially perpendicular to the distributor plates
  • Preferred axis directed and then distributed to the cooling channels. This is also intended to prevent feedback or mixing of air which has already been discharged with the air supplied for impingement cooling.
  • a baffle device with a perforated, trapezoidal, uniaxial corrugated sheet is similar to that described in EP 0 624 757 A1, US 5,467,815.
  • the baffle plate is arranged at a distance from a wall of a combustion chamber to be cooled. After impingement cooling of the wall by means of cooling air, the air reaches m areas of the wave crests with an enlarged flow cross-section, where the Air is passed along the axis. This does not prevent an impact on the baffle air from adjacent baffle holes, since an unimpeded overflow is possible.
  • the object of the invention is to provide an improved device for a component to be cooled, with a baffle cooling plate to which a coolant can be applied.
  • the device is intended in particular to bring about improved impingement cooling for the component to be cooled and to enable more efficient cooling.
  • this object is achieved by a device for a component to be cooled, with a baffle cooling plate which can be acted upon with a coolant and a coolant passage, the baffle cooling plate being arranged in front of the component to be cooled, with between the baffle cooling plate and the component to be cooled next to the coolant passage a discharge channel for the coolant is provided, and wherein the impact cooling plate has a further coolant passage, the discharge channel having a flow barrier for the coolant between the coolant passage and the further coolant passage.
  • a coolant In the case of impact cooling, a coolant is usually passed through a multiplicity of coolant passages in a plate or in a metal sheet (impact cooling sheet) which is adjacent to the surface to be cooled of the component to be cooled. As a result, the coolant impinges in a corresponding number of coolant jets essentially perpendicular to the surface to be cooled. When interacting with the surface to be cooled, the coolant absorbs heat which is transferred from the thermally loaded component to the coolant as a result of heat transfer. As a result of this interaction, the coolant heats up. The cow efficiency at the impingement cooling is higher than z. B.
  • the invention is based on the finding that in the conventional cooling concepts, which baffle a component by means of impingement cooling, which have a surface to be cooled, there are extensive areas underneath the impingement cooling plate between the latter and the component to be cooled along the surface to be cooled , m where there are high flow rates of the coolant.
  • the coolant flow takes place essentially perpendicular to the coolant jets, which expand in a nozzle shape from coolant feedthroughs in the impingement cooling plate in one direction against the surface of the component to be cooled.
  • the transversal flow around the coolant jets causes them to be sensitive to their nozzle jet character, in particular m the immediate vicinity of the surface of the component to be cooled, where this effect has a particularly disadvantageous effect.
  • the transversal flow when interacting with a coolant jet, leads to eddies that lower the average temperature of the coolant in the coolant jet. Compared to the case without a disturbing transverse flow, the cow's efficiency is reduced.
  • the invention shows a way to significantly reduce the transverse flow along an impact-cooled surface of a component in the region of the nozzle expansion of a coolant jet.
  • the device provides a discharge channel which discharges the coolant after the component has been impact-cooled.
  • the discharge channel points a flow barrier between the coolant feedthrough and a further coolant feedthrough. This significantly reduces the transversal flow in the area of the coolant jets.
  • the discharge channel is provided next to the coolant duct, so that the coolant reaches the discharge channel immediately after the component has been impact-cooled.
  • the flow of the coolant is thus channeled, and the impact cooling effect of the coolant jets, which expand in a nozzle shape from the coolant passages in one direction against the surface of the component to be cooled, is increased as a result of the reduced transverse flow.
  • the flow barrier according to the invention provides an area with a significantly reduced flow cross-section for the coolant between the coolant passage and a further coolant passage.
  • the flow barrier of the discharge channel can advantageously be designed in such a way that almost no direct flow of coolant from the coolant feedthrough to the further coolant feedthrough is possible. This largely reduces the mutual influence of coolant jets, which expand from the coolant passage through the further coolant passage in the shape of a nozzle jet to impingement cooling of the component. A transverse flow that adversely affects the impact cooling can not build up. A practically undisturbed nozzle jet expansion is guaranteed.
  • the discharge channel serves on the one hand as a collecting channel for the coolant and on the other hand as a flow channel.
  • the cooling means can be passed on to a desired area by means of the discharge channel between the impingement cooling plate and the component to be cooled and can be used for further cooling purposes.
  • the discharge channel can be designed in such a way that 1 this conducts the coolant along the component, in particular along the surface of the component, whereby convective cooling is achieved.
  • the coolant can be passed through the discharge channel to other areas of the same component in order to be used there for further cooling purposes. Furthermore, it is possible with the aid of the discharge channel to guide the coolant to a further component in order to use it there for cooling the further component.
  • the most useful cooling mechanisms here are, in addition to further impingement cooling, convective cooling and film cooling. The device thus enables a significant increase in efficiency in the impact cooling of a component and, in particular, a targeted possibility of further use of the coolant after the impact cooling.
  • a further coolant feedthrough is preferably provided, which lies opposite the coolant feedthrough beyond the discharge channel.
  • the additional coolant feed-through provides a further option for impact cooling of the component.
  • the discharge channel can be supplied with coolant from two sides.
  • the device is advantageously designed such that at least two coolant bushings are assigned to the discharge channel. It is therefore not necessary to provide a separate discharge channel for each coolant feedthrough.
  • a plurality of coolant feedthroughs is preferably arranged parallel to the discharge channel.
  • Several coolant feedthroughs are thus present along the discharge channel and assigned to this. This means that after the component has been impact-cooled by means of coolant jets from the coolant passages, the coolant reaches the discharge channel.
  • the discharge channel is fed by a plurality of coolant bushings with coolant. This means that the discharge channel is used very efficiently. As a result, a corresponding amount of coolant is collected and discharged in the discharge channel.
  • a plurality of discharge channels are provided. With a corresponding number and arrangement of coolant feedthroughs in the impact cooling plate, it is advantageous to have a plurality of discharge channels available.
  • the number and arrangement of discharge channels can thus be specifically and efficiently adapted.
  • the discharge channels are advantageously arranged over a large area along the surface of the component to be cooled by impact cooling.
  • the plurality of deflection channels ensures that the coolant is discharged from a coolant jet after the component has been impinged at least via a discharge channel. A transverse flow that would adversely affect the efficiency of the impact cooling is thus largely prevented in the area of the entire impact-cooled surface of the component.
  • the discharge channels preferably extend along a longitudinal axis.
  • the longitudinal axis thus forms a preferred direction along which the discharge channels preferably extend.
  • a plurality of discharge channels can advantageously be formed in parallel along the longitudinal axis.
  • the coolant can be passed on in a targeted manner along this longitudinal axis.
  • a sufficient amount of coolant m can thus be directed in a preferred direction, possibly for cooling the component or a further component adjacent to the component along the longitudinal axis.
  • the coolant can then be used there for further cooling purposes.
  • the discharge channel has a flow barrier for coolant between two adjacent coolant feedthroughs.
  • Two adjacent coolant feedthroughs are understood to mean two coolant feedthroughs which are arranged in succession along the drainage channel, the coolant feedthrough gen related to the discharge channel are arranged on the same side of the discharge channel.
  • the flow barrier creates an area with a significantly reduced flow cross section between the adjacent coolant feedthroughs.
  • the flow barrier is advantageously designed such that practically no further flow of coolant is possible from a first coolant passage to a second coolant passage adjacent to the first coolant passage. This largely reduces the mutual influence of coolant jets, which expand in a nozzle shape from the adjacent coolant feedthroughs for impact cooling of the component. In particular, a transverse flow that adversely affects the impact cooling efficiency can practically not build up. This configuration advantageously also achieves a more efficient supply of coolant to the discharge duct.
  • the discharge duct is preferably formed by the baffle cooling plate, in particular by a wave-shaped bend in the baffle cooling plate.
  • the discharge duct is therefore part of the baffle cooling plate. It is therefore advantageously not necessary to produce a separate additional component that forms the discharge channel and to equip the device with it.
  • Conventional devices for impingement cooling can therefore be equipped in a simple manner with an impingement cooling plate forming a discharge duct in order to achieve improved impingement cooling.
  • a conventional baffle cooling plate in a device for a component to be cooled can be replaced by the baffle cooling plate with the discharge duct. The costs of retrofitting are therefore negligible compared to the advantages of the new cooling concept.
  • the baffle cooling plate is preferably in one piece.
  • the baffle cooling plate is simple and by this design particularly inexpensive to manufacture.
  • the baffle cooling plate can be manufactured, for example, from a sheet metal blank using customary manufacturing methods, for example by deep drawing.
  • the coolant feedthroughs and the final shaping can take place, for example, by punching in a punching machine.
  • Due to the one-piece design the discharge duct with the flow barrier is an integral part of the baffle cooling plate. It is of great advantage that the discharge duct can be produced together with the impact cooling plate by appropriate shaping of the impact cooling plate.
  • the discharge channel can be made, for example, by undulating the baffle cooling plate. This eliminates the need for welding or other connections between the baffle plate and the discharge channel.
  • the wave-shaped bending can take place along two preferred axes, so that a relief-shaped wave structure with wave crests and wave troughs is formed in two dimensions.
  • a baffle plate designed in this way has a high thermomechanical elasticity and is particularly suitable for high-temperature applications, in particular in a gas turbine.
  • the baffle cooling plate has a deformation tolerance in several dimensions which is very advantageous for the high-temperature application.
  • the baffle cooling plate is preferably made of a high-temperature resistant material.
  • high-temperature-resistant steels or alloys based on nickel, iron or chrome are suitable as materials.
  • the component to be cooled is preferably a component of a thermal machine, in particular a gas turbine, which is exposed to high temperatures.
  • the component to be cooled is further preferably a platform of a turbine blade or a heat shield element of a combustion chamber of a gas turbine.
  • a turbi In addition to turbine blades, both turbine blades and turbine blades can be considered. Further applications of the device, for example for the impingement cooling of wall elements in the oven or for cooling of power and working machines, are possible.
  • the device for a component to be cooled is explained in more detail below with reference to the exemplary embodiments shown in the drawing. It shows schematically and simplified:
  • FIG. 1 shows a gas turbine with a compressor, combustion chamber and turbine
  • FIG. 2 shows a perspective illustration of a turbine guide vane with an impact cooling plate
  • FIG. 3 shows a view of a section of the turbine guide vane shown in FIG. 2 along the section line III-III
  • FIG. 4 shows a view of a section of the turbine guide vane shown in FIG. 2 along the section line IV-IV.
  • the gas turbine 1 shows a half section through a gas turbine 1.
  • the gas turbine 1 has a compressor 3 for combustion air, a combustion chamber 5 with a burner 7 for a liquid or gaseous fuel, and a turbine 9 for driving the compressor 3 and a generator (not shown in FIG. 1).
  • the turbine 9 there are fixed guide vanes 11 and rotatable rotor blades 13 on respective radially extending rings, not shown in half section, along the axis of rotation 19 of the gas turbine ⁇ arranged.
  • a consecutive pair along the axis of rotation 19 comprising a ring of guide vanes 11 (guide blade ring) and a ring of rotor blades 13 (rotor blade ring) is referred to as a turbine stage.
  • Each guide vane 11 has a platform 17, which is arranged to fix the relevant guide vane 11 to the inner turbine housing 23.
  • the platform 17 represents a wall element m of the turbine 9.
  • the platform 17 is a thermally highly stressed component 17, which forms the outer boundary for a hot medium M, in particular the hot gas duct 25, of the turbine 9.
  • the rotor blade 13 is fastened on the turbine rotor 27 arranged along the axis of rotation 19 of the gas turbine 1.
  • Em Fuhrungsrmg 15 is arranged as a wall element of the gas turbine 1 between the platforms 17 of two axially spaced, adjacent guide vanes 11.
  • the guide 15 and the platform 17 of the guide vane 11 each have a hot side 29 which is exposed to the hot medium M, in particular the hot gas M, during operation of the gas turbine 1.
  • the hot side 29 of the guide belt 15 is spaced radially from the outer end 21 of the rotor blade 13 by a gap.
  • the platform 17 of the guide vane 11 and the guide ring which axially adjoins the platform 17 each represent coolable components 17 which are acted upon by a coolant K for cooling.
  • the component 17 to be cooled in particular the platform 17 of the guide vane 11, is acted upon by a coolant K, in particular the cooling air K, from the side of the platform 17 opposite the hot side 29 of the platform 17 for cooling.
  • the platform 17 is cooled by means of impingement cooling.
  • FIG. 2 shows a perspective illustration of a turbine guide vane 11.
  • the turbine guide vane 11 has a platform 17 and an airfoil 39 connected to the platform 17.
  • the platform 17 has a hot side 29, to which a hot medium M is applied during operation of the gas turbine 1.
  • the platform 17 is a thermally highly stressed component 17, which is cooled by means of impingement cooling.
  • On the hot side 29 opposite side of the platform 17 a trough-shaped baffle plate 31 is arranged.
  • the impingement cooling plate 31 has an inflow side 41.
  • the impact cooling plate 31 is from the inflow side 41
  • Impact cooling of the platform 17 can be acted upon with a coolant K. This is indicated by thick arrows.
  • the impact cooling plate 31 is arranged in front of the platform 17 to be cooled.
  • the baffle cooling plate 31 has a hole-shaped coolant feedthrough 33, the coolant feedthrough 33 being one of a plurality of coolant feedthroughs 33.
  • a discharge duct 37 for the coolant K is provided between the baffle cooling plate 31 and the component 17 to be cooled, in particular the platform 17, in addition to the coolant passage 33.
  • the discharge duct 37 serves to discharge the coolant K after the impact cooling of the platform 17.
  • the impingement cooling plate 31 is acted upon by the coolant K on the inflow side 41 under high pressure.
  • the coolant K flows through the coolant passages 33 and forms according to the number and Arrangement of the coolant feedthroughs 33 a plurality of coolant jets on the side of the baffle cooling plate 31 facing away from the inflow side 41.
  • These coolant jets impact the platform 17, the coolant K absorbing heat from the platform 17, which is acted upon by the hot medium M due to the heat conduction Hot side 29 is directed to the side of platform 17 opposite hot side 29.
  • the coolant K is heated, the temperature of the coolant K increasing accordingly.
  • the coolant K is discharged through the discharge channel 37.
  • the coolant K is passed on to different areas of the platform 17 in a targeted manner.
  • the coolant K is preferably used for further cooling of the platform 17 or a further component adjacent to the platform 17 and not shown in FIG. 2.
  • convective cooling or film cooling come into question as cooling mechanisms.
  • the coolant K is guided through a suitable passage channel 35 of the platform 17.
  • the coolant K flows through the passage channel 35 to the further component for cooling the same.
  • the passage channel 35 is, for example, a simple hole in the platform 17.
  • FIG. 3 shows a view of a section of the turbine guide vane 11 shown in FIG. 2 along the section line
  • the baffle cooling plate 31 comprises a corrugated wall 51 with an inflow side 41 which can be acted upon by the coolant K and an outflow side 45 opposite the inflow side 41.
  • a cooling region 47 adjoins the outflow side 45, the area between the cooling surface 43 of the component 17 to be cooled and the outflow side 45 is formed.
  • the wall 51 has a plurality of the wall 51 penetrating ⁇ Coolant feedthroughs 33. The coolant feedthrough 33 is followed in the cooling area 47 by a nozzle expansion area 49.
  • a discharge channel 37 for cooling agent K is formed along the wall 51.
  • the discharge channel 37 is arranged next to the coolant passage 33.
  • the discharge duct 37 is one of a plurality of discharge ducts 37, and the coolant passage 33 is one of a plurality of coolant passages 33.
  • the discharge duct 37 is formed by the baffle cooling plate 31 and extends parallel to a longitudinal axis 53.
  • the baffle cooling plate 31 is made in one piece with the discharge duct 37.
  • the baffle cooling plate 31 is arranged such that the downstream side 45 of the baffle cooling plate 31 is opposite the cooling surface 43 of the platform 17.
  • the hot side 29 of the platform 17 is acted upon by the hot medium M, in particular the hot gas M.
  • the platform 17 In order to withstand the high temperatures, the platform 17 must be cooled.
  • the inflow side 41 of the impingement cooling plate 31 is acted upon by the cooling agent K under suitable pressure.
  • the coolant K reaches the nozzle expansion area 49 from the inflow side 41 through the coolant passages 33.
  • the coolant K expands in the nozzle expansion area 49 in the shape of a jet in the direction of the platform 17 to be cooled and strikes a plurality of coolant jets against the cooling surface 43 Platform 17 efficiently impact-cooled on the cooling surface 43.
  • the cooling agent K absorbs heat which is transported as a result of the heat conduction from the hot side 29 to the cooling surface 43 opposite the hot side 29.
  • the coolant K heats up.
  • the coolant K is collected in the discharge duct 37; it and is available for further cooling purposes.
  • the coolant K can be derived parallel to the longitudinal axis 53 and optionally used for cooling the platform 17 in another area and / or for cooling a further component, which is not shown in more detail in FIG.
  • the further component can be, for example, a platform 17 of a further turbine guide vane 11 or a guide 15 (see FIG. 1).
  • the convective cooling and the film cooling can be used as cooling mechanisms.
  • the plurality of discharge ducts 37 ensures that the coolant K is discharged from the nozzle expansion region 49 after the impingement cooling of the platform 17 via at least one of the discharge ducts 37. A flow transverse to the coolant jets along the cooling surface 43, which would adversely affect the efficiency of the impingement cooling, can thus be largely reduced in the nozzle expansion region 49.
  • FIG. 4 shows a view of a section of the turbine guide vane 11 shown in FIG. 2 along the section line IV-IV.
  • the section line IV-IV is axially arranged along the longitudinal axis 53 of the section lines III-III (see FIG. 3).
  • the section line IV-IV forms a transverse axis that extends essentially perpendicular to the longitudinal axis 53 and along which no coolant passage 33 is arranged.
  • the discharge channel 37 has one
  • the discharge duct 37 with the flow barrier 55 is formed by the impingement cooling plate 31.
  • the flow barrier 55 is designed such that the downstream side 45 of the baffle plate 31 is in contact with the cooling surface 43 of the platform 17 m.
  • the flow barriers 55 for coolant K are formed between two coolant feedthroughs 33 adjacent along the longitudinal axis 53.
  • Two adjacent coolant feedthroughs 33 are understood to mean two coolant feedthroughs 33 which are arranged in succession along the discharge channel 37.
  • the flow bar 55 seals off the nozzle expansion areas 49 which are respectively assigned to the adjacent coolant feedthroughs 33. This prevents an overflow of coolant K from a nozzle expansion region 49 to a further nozzle expansion region 49 adjacent along the longitudinal axis 53.
  • the invention is characterized in that a significantly improved impingement cooling is made possible for the component to be cooled, as well as more efficient use of coolant compared to conventional impingement cooling arrangements.
  • the baffle cooling plate is designed in a suitable manner so that a transverse flow, in particular in the nozzle expansion area of the coolant jets, is largely prevented in the cooling area which is formed between the baffle cooling plate and the component to be cooled.
  • the specified cooling concept allows the component with a lower cooling agent consumption to be kept at a specified material temperature. This increase in efficiency is associated with an increase in efficiency when using the device in a thermal machine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un dispositif destiné à un composant (17) à refroidir devant lequel est placée une tôle de refroidissement par choc (31) qui peut être soumise à l'action d'un agent de refroidissement (K) et qui comporte au moins un passage pour agent de refroidissement (33). Entre la tôle de refroidissement par choc (31) et le composant (17) à refroidir, un canal de dérivation (37) destiné à l'agent de refroidissement (K) est situé à côté du passage pour agent de refroidissement (33). Ainsi l'agent de refroidissement (K) arrive, lorsque le composant (17) a été refroidi par choc, dans le canal de dérivation (37). Au moyen de ce canal de dérivation (37), l'agent de refroidissement (K) est collecté, dérivé et il peut être utilisé de façon ciblée à d'autres fins de refroidissement. Ce dispositif permet d'obtenir un refroidissement par choc efficace.
PCT/EP2000/007387 1999-08-03 2000-07-31 Dispositif de refroidissement par choc WO2001009553A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US10/048,822 US6659714B1 (en) 1999-08-03 2000-07-31 Baffle cooling device
JP2001513790A JP2003532821A (ja) 1999-08-03 2000-07-31 構造部品の冷却装置
DE50008555T DE50008555D1 (de) 1999-08-03 2000-07-31 Prallkühlvorrichtung
EP00956359A EP1409926B1 (fr) 1999-08-03 2000-07-31 Dispositif de refroidissement par choc

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP99115330 1999-08-03
EP99115330.5 1999-08-03

Publications (1)

Publication Number Publication Date
WO2001009553A1 true WO2001009553A1 (fr) 2001-02-08

Family

ID=8238719

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2000/007387 WO2001009553A1 (fr) 1999-08-03 2000-07-31 Dispositif de refroidissement par choc

Country Status (5)

Country Link
US (1) US6659714B1 (fr)
EP (1) EP1409926B1 (fr)
JP (1) JP2003532821A (fr)
DE (1) DE50008555D1 (fr)
WO (1) WO2001009553A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002048527A1 (fr) * 2000-12-11 2002-06-20 Pratt & Whitney Canada Corp. Double refroidissement successif pour turbine/chambre de combustion

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2907841B1 (fr) * 2006-10-30 2011-04-15 Snecma Secteur d'anneau de turbine de turbomachine
US8152468B2 (en) * 2009-03-13 2012-04-10 United Technologies Corporation Divoted airfoil baffle having aimed cooling holes
GB0916432D0 (en) * 2009-09-21 2009-10-28 Rolls Royce Plc Separator device
FR2955890B1 (fr) * 2010-02-02 2013-08-16 Snecma Secteur d'anneau de turbine de turbomachine
RU2530685C2 (ru) * 2010-03-25 2014-10-10 Дженерал Электрик Компани Структуры ударного воздействия для систем охлаждения
US9347324B2 (en) * 2010-09-20 2016-05-24 Siemens Aktiengesellschaft Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles
US20120070302A1 (en) * 2010-09-20 2012-03-22 Ching-Pang Lee Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles
US8714911B2 (en) * 2011-01-06 2014-05-06 General Electric Company Impingement plate for turbomachine components and components equipped therewith
US9719372B2 (en) 2012-05-01 2017-08-01 General Electric Company Gas turbomachine including a counter-flow cooling system and method
US9719362B2 (en) 2013-04-24 2017-08-01 Honeywell International Inc. Turbine nozzles and methods of manufacturing the same
US10100737B2 (en) * 2013-05-16 2018-10-16 Siemens Energy, Inc. Impingement cooling arrangement having a snap-in plate
US9976441B2 (en) * 2015-05-29 2018-05-22 General Electric Company Article, component, and method of forming an article
PL232314B1 (pl) 2016-05-06 2019-06-28 Gen Electric Maszyna przepływowa zawierająca system regulacji luzu
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US20180066539A1 (en) * 2016-09-06 2018-03-08 United Technologies Corporation Impingement cooling with increased cross-flow area
US10914192B2 (en) * 2018-09-25 2021-02-09 Raytheon Technologies Corporation Impingement cooling for gas turbine engine component
WO2023121680A1 (fr) * 2021-12-20 2023-06-29 General Electric Company Filtre à particules à tamis métallique pour profil aérodynamique de turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
US5467815A (en) * 1992-12-28 1995-11-21 Abb Research Ltd. Apparatus for impingement cooling
EP0690205A2 (fr) * 1994-06-30 1996-01-03 General Electric Company Dispositif de refroidissement d'une virole de turbine
EP0905353A1 (fr) * 1997-09-30 1999-03-31 Abb Research Ltd. Elément de paroi refroidi par jet

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1079131B (it) 1975-06-30 1985-05-08 Gen Electric Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
JPH0756201B2 (ja) 1984-03-13 1995-06-14 株式会社東芝 ガスタービン翼
US4642024A (en) 1984-12-05 1987-02-10 United Technologies Corporation Coolable stator assembly for a rotary machine
US5083422A (en) 1988-03-25 1992-01-28 General Electric Company Method of breach cooling
US5649806A (en) 1993-11-22 1997-07-22 United Technologies Corporation Enhanced film cooling slot for turbine blade outer air seals
JPH08338203A (ja) * 1995-06-09 1996-12-24 Hitachi Ltd ガスタービン静翼

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5467815A (en) * 1992-12-28 1995-11-21 Abb Research Ltd. Apparatus for impingement cooling
EP0624757A1 (fr) * 1993-05-10 1994-11-17 General Electric Company Refroidissement récuperatif par impact de jet d'air pour composants de moteur à réaction
EP0690205A2 (fr) * 1994-06-30 1996-01-03 General Electric Company Dispositif de refroidissement d'une virole de turbine
EP0905353A1 (fr) * 1997-09-30 1999-03-31 Abb Research Ltd. Elément de paroi refroidi par jet

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002048527A1 (fr) * 2000-12-11 2002-06-20 Pratt & Whitney Canada Corp. Double refroidissement successif pour turbine/chambre de combustion
US6536201B2 (en) 2000-12-11 2003-03-25 Pratt & Whitney Canada Corp. Combustor turbine successive dual cooling

Also Published As

Publication number Publication date
EP1409926A1 (fr) 2004-04-21
US6659714B1 (en) 2003-12-09
DE50008555D1 (de) 2004-12-09
JP2003532821A (ja) 2003-11-05
EP1409926B1 (fr) 2004-11-03

Similar Documents

Publication Publication Date Title
WO2001009553A1 (fr) Dispositif de refroidissement par choc
EP1005620B1 (fr) Element constitutif d'un bouclier thermique a recirculation du fluide de refroidissement
EP0244693B1 (fr) Dispositif protecteur contre le surchauffage à gaz chaud pour les propulseurs à turbine à gaz
DE69816532T2 (de) Wärmeübergangsstruktur
EP0899425B1 (fr) Aube pour une turbine à gaz
EP1386070B1 (fr) Procede de refroidissement d'une turbine a gaz, et installation de turbine a gaz
EP1276972B1 (fr) Turbine
EP1505254B1 (fr) Turbine à gaz et méthode pour la refroidir
DE102008002890A1 (de) Wechselseitig gekühltes Turbinenleitrad
EP1836442A1 (fr) Ecran thermique
DE2943464A1 (de) Dichtungsvorrichtung fuer ein gasturbinentriebwerk
DE2844701A1 (de) Fluessigkeitsgekuehlter turbinenrotor
EP2084368B1 (fr) Aube de turbine
EP2184445A1 (fr) Support d'aubes statorique axialement segmenté d'une turbine à gaz
EP1245806A1 (fr) Aube de turbine refroidie
EP1656497A1 (fr) Diffuseur situe entre le compresseur et la chambre de combustion d'une turbine a gaz
EP1165942B1 (fr) Turbomachine avec un systeme d'elements de paroi pouvant etre refroidi et procede de refroidissement d'un systeme d'elements de paroi
EP1268981B1 (fr) Installation de turbine
EP1249578A1 (fr) Refroidissement d'une turbine à gaz
EP2347100B1 (fr) Turbine à gaz avec insert de refroidissement
DE112014006619B4 (de) Gasturbinenbrennkammer und mit selbiger versehene Gasturbine
WO2004031656A1 (fr) Turbine a gaz
WO2010023123A1 (fr) Support d'aubes directrices pour une turbine à gaz et procédé permettant de faire fonctionner une turbine à gaz
WO2006072528A1 (fr) Turbine a gaz comportant un generateur de prerotation et procede d'utilisation d'une turbine a gaz
WO2004109187A1 (fr) Element de protection thermique

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): CA CN IN JP KR US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE

121 Ep: the epo has been informed by wipo that ep was designated in this application
DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
WWE Wipo information: entry into national phase

Ref document number: 2000956359

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 10048822

Country of ref document: US

WWP Wipo information: published in national office

Ref document number: 2000956359

Country of ref document: EP

WWG Wipo information: grant in national office

Ref document number: 2000956359

Country of ref document: EP